Aircraft



y 1942- .1. WEICHWALD 2,291,515

AIRGRAFT 7 Filed Nov. 13, 1939 '7 Sheets-Sheet 2 A-B Hg. 2 5-0 I I IWWW/M INVENTOR.

y 1942- J. WEICHWALD 2,291,515

AIRCRAFT Filed Nov. 15, 1939- 7 Sheets-Sheet 3 o I o 0 D) Em INVENTOR.

y 28,1942. J. WEICHWALD 2,291,515

AIRCRAFT Filed Nov. 13, 1939 '7 Sheets- Sheet 7 INVENTOR.

Patented July 28, 1942 1 UNITED STATES PATENT OFFICE AIRCRAFT JohnWeichwald, Chicago, 111.

Application November 13, 1939, Serial No. 304,261

3 Claims.

This invention relates generally to air craft and has particularreference to new and useful improvements in flying machines of theheavier-than-air type.

This application is a refile in part of my abandoned application SerialNo. 185,904 filed Jan. 20, 1938.

One of the objects of my invention resides in the provision of a flyingmachine having a fuselage provided with a combined rudder and elevator.a centrally disposed power-driven propeller and a plurality oflongitudinally and transversely spaced power-driven propellers but nolaterally disposed wings or aerofoils.

Another object of my invention resides in the provision of a novelpower-propelled flying machine having a novel construction andarrangement of members and parts whereby the required pendulousstability is provided to insure the necessary equilibrium of the machineduring its ascent, flight, and descent. Among the novel featurescontributing to the pendulous stability through which the equilibrium ofthe craft is attained are:

(a) Fuselage design having an enlarged or extended body portionextending substantially below the longitudinal axis of the fuselage;

(b) The upper portion of the fuselage being constructed of comparativelylight weight material and the lower portion of the fuselage beingWeighted and constructed of considerably heavier materials tosubstantially increase the weight of the fuselage below its longitudinalaxis so that the center of gravity is substantially lowered to providethe desired flight-sustaining equilibrium of the body;

The provision of storage tanks for the oil and fuel or gasoline withinthe extended weighted lower portion of the fuselage;

(d) The extended elevator planes;

(e) The plurality of longitudinally aligned and transversely spacedpairs of motors.

With the above and other objects in View, my invention consists in thenovel construction and arrangement of the parts and members shown inpreferred embodiment in the attached drawings, described in thefollowing specification, and particularly pointed out in the appendedclaims.

Referring to the drawings:

Figs. 1, 2, and 3 show plan views of sections A, B, and C of the craft,or respectively, the forward or front end portion, the intermediateportion, and the rear portion of the fuselage;

Figs. 4, 5, and 6 are side elevations of sections A, B, and Crespectively, shown in Figs. 1, 2, and 3; and

Fig. 7 is a plan view of a flying craft or machine embodying myinvention.

Referring to Figs. 1 and 4, showing respectively a plan view and sideelevation of the front portion, or section A of the craft, the crankcasehousing is indicated by numerals 2 and 3.

and the motor-supporting swivel frames are indicated by numeral l.

The two laterally spaced sets of vertical and horizontal cross-bars 5are connected at their inner ends to the extensions 4 of the swivelframes l. The two sets of bars 5 are connected together bylongitudinally extending connecting members I and 8. The swivelframe-supporting structure includes the diagonal braces 6 for thecross-bars 5.

9 indicates studs which extend through the swivel frames I and crankcase covers. The bolts Ill connect the swivel frame cross-bars 5 withthe longitudinal bars 1 and 8.

A bracket I2 is rigidly connected to the rear end ll of the crank-casehousing 3.

The two links I3 are pivotally connected to the bracket l2 and theopposite ends H: of these links are formed into right-angularly disposedshort ends positioned in ball-bearing rollers I4 which are adapted toride up and down within the channeled guide rails It which are suitablyheld in fixed position on the supports El and H3.

The front motor tilting mechanism includes a horizontal shaft l9 havinga pair of vertically disposed end members 20 pivotally connected by pins26 to the upper ends of the links 2|. The lower ends of links 2| arepivotally connected by pins 26 to the lower ends of the verticallydisposed rocker arms 22 which are pivotally supported on pins 25.

The upper ends of the rocker arms 22 are pivotally connected by pins 26with the upper ends of the links 23 the lower ends of which arepivotally connected to the outer ends of the arms 24. I

The front ends of arms 24 are securely fastened to the members 8. Thetwo side members 8 are provided with pivot pins 30 which are pivotallymounted in the flanged bearings 2'! and bolts 28 and 29 secure thebearings 21 to the centrally converging end of the craft housing 35.

The pivotal supports 30 are reenforced by the angularly disposedstructural braces 3i and 32 and these braces 3| and 32 are connected byrigid braces 33 and 34 and secured by bolts 38 to the cross partition39. The closure head or housing for the open end of the craft body isindicated by 36.

As an additional support for the pivot pins 25, I provide a pair ofrigid bars 31 which are secured to the bottom of the craft and extend incurved form upwardly along the sides of the craft housing up to thepivotal pins 25.

In order to maintain a closure at the lower or bottom end of the closurehead or housing for the open end of the craft body during the upwardtilting of the motor about the pivots 30, the motor housing 36 isprovided with a pair of hingedly connected closure sections 40 and 40which are provided with hinges at 4I A and M The ground or landingwheels 45 are pivoted for the operating wire ropes 83.

at 44 upon the legs 43 which are secured by bolts 42 to the craftstructure.

Referring now to Figs. 2 and 5 which show respectively a plan view andside elevation-of the central or intermediate section of the craftindicated as -B, the body portion 46 includes the structural reenforcingmembers 39 which extend vertically of the body sides and transversely ofthe body.

The side extensions 50 of the-instrument board enclose the oil feed tankO'and the gasoline 'feed tank G. The broken lines 5|, 52, and 53indicate respectively the door, its hinges, and the operatorsseats.

To insure pendulous stability thebottom'of the craft is extended incurved form, as at 55, and weighted as indicated at 56 with a mass ofconcrete 'orsteel to lower the'center of gravity below the longitudinalaxis of the craft body.

-As additional means for lowering the center of gravity to therebyinsure the pendulousstability of the craft, there are provided below thecraft floor 54, storage tanks for oil and gasoline, respectively,indicated by numerals 51 and 64.

The oil-storage tank-51 is provided with an'oil inlet 58, an outletconnection 59, anda connection 60 for an overflow pipe.

Suitable steel-straps 6| secure the oil tank 51 and gasoline storagetank 64 to thesupporting wood blocks 63 which are secured to the craftstructure by-angle irons 62.

The main gasoline storage tank -64 is provided with-an inlet closure cup66 and an outlet-connee-tion 65. The-craft-body has a suitable door toprovide access to the tank inlet as indicated by the broken lines 61.The tank 64 is also provided with steel straps 6| which are secured tothe woods blocks 63 which are -held in place by the angle irons-62.

' The oil and gasoline tanks are provided with drains indicated by 68.

The control pit is indicated by -69,-see Fig. 2. The two verticallydisposed rudder -control shafts 10 are supported at their lower ends insuitable bearings H and their upper ends are provided withright-angularly bent integral portions 1.3 terminating in pivotedhandles 14.

The shafts 1-0 are mounted in supporting split housings 80 securedtogether by bolts 8| and having'fioor flanges 86 which are riveted tothefioor 54. Each operating handle 14 is provided with a triangularlock-pin operator 16 pivoted to the handle 14 and which is adapted to begripped with the handle 14 to raise the lock-pin 11, against thepressure of the coil'spring '18, out of one of the circularly arrangedholes in the semicircular plate portion 19 at the top of the housing 80to release the handle 14 for rudder-operating movement. A leafspring ismounted between the operator lever 16 and the handle 14 circular collars12 formed integrally with the shaft 1.0.

Trained around each sprocket 96 is a sprocket chain or perforated steelband 82 and to the ends of which are connected the Wire ropes 83 foroperating the rudders I05 and H0.

Tension adjusting turnblocks 84 are provided The operating ropes 83 areguided in suitable pivoted guides 85.

The front motor-tilting operating lever 88 is connected to the operatingshaft I9 whereby same is rotated on the support 81 to cause a tilting ofthe front motor through the two sets of parts 20, 2I, 22, 23, and 24.The motor rear-end guiding and tilting means is indicated by referencenumerals I2 to I6 inclusive.

The 'opera'tinghandle 88 is provided with lockrod '91 which is mountedin guides 93 and the lower end of the lock-rod 9| is adapted to beseated between any pair of the teeth on the quadrant 81 to retain thelever 88 and :motor 'in the selected tilted position.

The lock-rod 9| is normally retained in locked position by 0011- spring92. The lock-rod tri'angular operating 'lever90 is pivoted on the handle88 and normally retained in locked position by the bent leaf spring 89.To release the lock-rod 3| handle -88 and lever are grasped in hand sothat lever 90 is moved against the pressures of the springs 89 and S2 tomove the end 'of lockrod 9| out of locked position with quadrant 81. Thequadrant is-secured by bolts 94' to the instrumerit board. 7

Windows are indicated by broken lines 95.

In Fig. 5 the preferable type "of closed body is indicated by 41 and theopen type of body is indicated by 48.

Even if all gasoline and oil were=eonsumed, the craftbody is so designedthat -its-centerof-g rav-ity is still substantially below thelongitudinal axis of the body. 7

Referring now particularly to Figs. 3 and 6 which show respectively planview and elevation of the rear end or section C of the craft-the rearend 91 is provided withan upper recessed portion 98 and a verticalstationary rudder portion 99 is secured'to the top of the rear -'endcraft'body'by angle irons -I 09.

The vertical movable rudder portion I 05 is hingedly supported on thehinge rod I'0I and hinge plates I04 secured to the stationary verticalrudder portion 99. The hinge rod I 0 I =-is supported-at its 1ower-endin a suitable bearing I00.

The stationary and -movable rudder portions extend a substa-ntialdi-s'tance above the top of the craftbody.

The vertical movable rudder portion -I-05 is also supported oncomparatively heavy hinges I03 connected to the craft recesse'd-endabove the shoulder I 02 of the rod WI.

The combined stabilizing horizontal *rudder, aerofoil-andfelevator-H 0includes a pair o'f la-tera-l stationary wings-or aero'foils l01 and-I08 which are suitably secured to the side of the craft body as byangle irons I0'9.

The hinge shaft I I I is provided with-a heavy central-hinge 1-03 andside h'in'ges I04 whichare secured to the horizontalstationarystabilizmg wings I01 and "I 08 and tothe movable horizontalelevator and stabilizer H 0.

The lateral lateral stationary wings I01 and I08 and the movablehorizontal elevator H are disposed in a horizontal plane which coincideswith the longitudinal center-line of the craft body which passes throughthe longitudinal center-line of the front or central propeller shaft.The wings I01 and I08 extend forwardly of the craft body andtransversely beyond the sides of the craft body.

The rudder-operating cables or ropes 83 extend through the flooropenings H3 and body openings 2 for connection to the rudder connectorsI06, as shown in Figs. 3 and 6.

The rear end running gear or wheel H5 is mounted on the axle H6supported in the rotatable leg II! which is secured as at H8 to thebracket I I4 connected by rivets or bolts I I9 to the craft framework.

The craft herein disclosed is provided with a plurality of propellersdriven by individual motors. One central motor is provided at the frontend of the body and two or more motors are provided on each side of thebody. All of the motors are mounted on tiltable supports which aresimilar in construction to that of the front or central motor. Anysuitable type of motor may be used but I prefer the radially disposedpiston type. The motors may be arranged to be tilted simultaneously orindividually controlled for independent tilting operation. Any suitablemeans for controlling the flow of the fuel through suitable carburetorsmay be provided.

The pivots for all propeller motors are disposed on a horizontal planewhich passes through the longitudinal center-line of the front orcentral propeller shaft.

As shown in the drawings, and referring particularly to Fig. 2, thevertical and horizontal movable rudder portions are independentlycontrolled by the two control handles 14. The upper one of the handlesI4, as shown in Fig. 2, controls the movable horizontal rudder portionand the lower one of the handles 14 controls the movable vertical rudderportion.

Various changes and modifications in the details of construction shownin the attached drawings by way of example may be made by those skilledin the art without departing from the spirit of my invention defined inthe appended claims.

It is to be understood that I do not intend to abandon any of my rightsfor various novel features shown herein and in my former abandonedapplication Serial No. 185,904 filed January 20, 1938, but not claimedherein as separate applications for such novel features may be filedlater. It is my intention to claim in this application the moreimportant features of my invention.

I claim:

1. In an aircraft, a body having an open front end defined byspacedparallel side walls and spaced parallel top and bottom walls, said sidewalls having extensions disposed beyond said top and bottom walls,pivotal supports on said side wall extensions, a closure head for theopen end of said body, a frame secured to the outer end of said closurehead pivotally mounted on said supports, a motor supported on saidframe, and means within said body for tilting said motor, frame andclosure head about said pivotal supports.

2. In an aircraft as defined in claim 1 and including closure plateshingedly connected to the bottom of said closure head, movable with butrelatively to said closure head, and constituting an extensible closurewhereby the open end of the body is maintained closed during the upwardtilting of the motor, frame and closure head.

3. In an aircraft structure as defined in claim 1 and including saidbody side walls having relatively converging rear extensions; said bodytop and bottom walls having relatively converging rear extensions; anupper portion of the rear end of the craft body above the longitudinalaxis of the body being recessed to provide a pair of relativelylongitudinally and vertically oifset upper and lower vertically disposedtransverse walls, said upper transverse wall extending above thelongitudinal axis of the craft body, said lower transverse wallextending below the longitudinal axis of the craft body; a stationaryvertical rudder mounted on the rear portion of said top wall and havinga vertical rear edge substantially vertically aligned with said uppertransverse wall; a movable vertical rudder, hingedly connected to saidstationary vertical rudder, extending into said recessed rear end andabove the longitudinal axis of the craft body; a combined horizontalstationary rudder and aerofoil disposed substantially in the plane ofthe longitudinal axis of the craft body and extending transversely ofand beyond the sides of the craft body, said horizontal stationaryrudder and aerofoil having plane-aligned extensions extending forwardlyof and along the rear portions of said body side walls and the rear edgeof said horizontal stationary rudder and aerofoil being substantially invertical alignment with said lower vertical transverse wall; a normallyhorizontally disposed tiltable elevator adapted for planealignment withsaid combined horizontal stationary rudder and aerofoil and hingedlyconnected thereto, said elevator being hinged substantially in the planeof the upper edge of said lower vertical transverse wall to extendrearwardly thereof and beyond the rear end of said movable verticalrudder; means for moving said vertical rudder; and means for tiltingsaid elevator.

JOHN WEICI-IWALD.

